Method and system for providing sealing in gas turbines

ABSTRACT

A gas turbine system is provided that includes a compressor section, a combustor assembly coupled to the compressor section, and a turbine section coupled to the compressor section. At least one of the combustor assembly and the turbine section includes a sealing sub-system for use in sealing between a first component and a second component. A first component defines a first seal member receiving region oriented between a higher-temperature gas region and a cooler-temperature gas region. A second component adjacent the first component defines a second seal member receiving region oriented adjacent the first seal member receiving region. The sealing system includes first and second end walls defined in at least one of the first and second seal member receiving regions. A seal member is oriented within the first and second seal member receiving regions, and includes at least a first layer defining at least a first resilient seal end portion that engages one of the first and second end walls.

FEDERAL RESEARCH STATEMENT

The subject matter of this disclosure was made with Government supportunder Contract No. DE-FC26-05NT42643, awarded by the Department ofEnergy (DOE), and the Government has certain rights in the subjectmatter claimed herein.

BACKGROUND

The present disclosure relates generally to rotary machines, and, morespecifically, to methods and systems for providing sealing betweencomponents within a gas turbine engine.

At least some known gas turbine engines include a plurality of sealassemblies that facilitate isolating a flow of combustion gaseschanneled along a fluid flow path (“hot gas path”) from cooler regionsof the gas turbine located between an inner shell of the gas turbineengine and components directly exposed to the lower-pressure combustiongas flow, for example. At least some known seal assemblies extendbetween adjacent stationary components, such as stator segments, withina stage of the gas turbine engine to provide sealing between ahigh-pressure, lower-temperature area and a low-pressure,higher-temperature area. To further protect against ingestion ofhigher-temperature combustion gases into the cooler regions of theengine, in at least some known gas turbine engines, purge air ischanneled into the cooler regions, at a pressure that is higher than apressure of the combustion gas flow.

At least some known seal assemblies include an elongated substantiallyplanar seal member that is inserted within adjacent elongatedrectangular slots or seal member receiving regions defined within twoadjacent components. Such seal members are sometimes referred to as“spline seals” and include side edge regions and end edge regions. In atleast some known seal assemblies, the adjacent rectangular slots arelonger in length than the seal member inserted within the slots, toaccommodate manufacturing tolerances and minor part-to-partmisalignments. In at least some known gas turbine engines that includesuch seal members, leakage of purge gases may occur around the end edgeregions of the seal members, specifically between the end edge regionsand the adjacent end regions of the elongated rectangular slots. As aresult of the leakage, a larger volume of purge air may be needed toensure that ingestion of combustion gases into the cooler regions isprevented, than would be needed if the leakage did not occur.

BRIEF DESCRIPTION

In one aspect, a method for providing a seal between components within agas turbine is provided. The method includes inserting a seal memberinto a first seal member receiving region defined within a firstcomponent of a gas turbine, wherein the first seal member receivingregion is oriented between a higher-temperature gas region and acooler-temperature gas region. The method also includes inserting theseal member into a second recess defined within a second component ofthe gas turbine, wherein the second component is adjacent to the firstcomponent, and wherein at least one of the first and second seal memberregions includes a first end wall and at least one of the first andsecond seal member regions includes a second end wall orientedsubstantially opposite the first end wall. The seal member includes atleast a first layer defining at least a first seal end portion thatengages one of the respective first and second end walls.

In still another aspect, a gas turbine system is provided. The gasturbine system includes a compressor section, a combustor assemblycoupled to the compressor section, and a turbine section coupled to thecompressor section. At least one of the combustor assembly and theturbine section includes a sealing sub-system for use in sealing betweena first component and a second component. The sealing sub-systemincludes a first component defining a first seal member receiving regionoriented between a higher-temperature gas region and acooler-temperature gas region. The sealing sub-system also includes asecond component adjacent the first component. The second componentdefines a second seal member receiving region oriented adjacent thefirst seal member receiving region, wherein at least one of the firstand second seal member receiving regions includes a first end wall. Atleast one of the first and second seal member receiving regions alsoincludes a second end wall oriented substantially opposite the first endwall. The sealing sub-system also includes a seal member oriented withinthe first and second seal member receiving regions, wherein the sealmember includes at least a first layer defining at least a firstresilient seal end portion that engages one of the first and second endwalls.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic illustration of an exemplary gas turbine engine.

FIG. 2 is a perspective view of an exemplary sealing system that may beused in the gas turbine engine shown in FIG. 1.

FIG. 3 is a side sectional view of the sealing system shown in FIG. 2.

FIG. 4 is an end sectional view of the sealing system shown in FIG. 3.

FIG. 5 is a side sectional view of an alternative sealing system thatmay be used in the gas turbine engine shown in FIG. 1.

FIG. 6 is a side sectional view of another alternative sealing systemthat may be used in the gas turbine engine shown in FIG. 1.

FIG. 7 is a side sectional view of yet another alternative sealingsystem that may be used in the gas turbine engine shown in FIG. 1.

FIG. 8 is a perspective view of yet another alternative sealing systemthat may be used in the gas turbine engine shown in FIG. 1.

DETAILED DESCRIPTION

As used herein, the terms “axial” and “axially” refer to directions andorientations extending substantially parallel to a longitudinal axis ofa gas turbine engine. Moreover, the terms “radial” and “radially” referto directions and orientations extending substantially perpendicular tothe longitudinal axis of the gas turbine engine. In addition, as usedherein, the terms “circumferential” and “circumferentially” refer todirections and orientations extending arcuately about the longitudinalaxis of the gas turbine engine. It should also be appreciated that theterm “fluid” as used herein includes any medium or material that flows,including, but not limited to, gas and air.

FIG. 1 is a schematic illustration of an exemplary gas turbine gasturbine engine 100. Gas turbine engine 100 includes a compressorassembly 102 and a combustor assembly 104. Gas turbine engine 100 alsoincludes a turbine assembly 108 and a common compressor/turbine shaft110 (sometimes referred to as a rotor 110), configured for rotationabout an axis 106.

In operation, air flows through compressor assembly 102 such thatcompressed air is supplied to combustor assembly 104. Fuel is channeledto a combustion region and/or zone (not shown) that is defined withincombustor assembly 104 wherein the fuel is mixed with the air andignited. Combustion gases generated in combustor assembly 104 arechanneled along a hot gas path 111 through turbine assembly 108 whereingas stream thermal energy is converted to mechanical rotational energy.

FIG. 2 is an enlarged perspective view of an exemplary sealing system200 that may be used in gas turbine gas turbine engine 100 (shown inFIG. 1). FIG. 3 is a side sectional elevational view of sealing system200, and FIG. 4 is an end sectional view of sealing system 200. Sealingsystem 200 is used to provide sealing between a first static component202 and an adjacent second static component 203. Seal member 204 extendsalong substantially the same direction as hot gas path 111.

In the exemplary embodiment, a seal region 206 is defined between anelongated slot or seal member receiving region 208 defined withincomponent 202, and a corresponding slot or seal member receiving region230 defined within component 203. A seal member 204 is captured (i.e.,at least partially inserted) within slots 208 and 230.

In the exemplary embodiment, sealing system 200 includes a plurality ofseal members, for example, seal members 209 and 213, in addition to sealmember 204, wherein seal members 209 and 213 are received in slots orseal member receiving regions 207 and 211, respectively. The arrangementof slots 207, 208, and 211 is exemplary only. In an alternativeembodiment, slots 207, 208 and 211 may be oriented in any configurationthat enables sealing system 200 to function as described herein.Moreover, each seal member 204, 209 and/or 213 may have anyconfiguration, including configurations that are different from eachother, which enables sealing system 200 to function as described herein.

In the exemplary embodiment, seal member 204 is a multi-layer sealmember that includes layers 210, 212, 214, 216, and 218. In oneembodiment, at least one of layers 210-218 is a solid metal layer.Moreover, in one embodiment, at least one of layers 210-218 is a metalcloth layer. Alternatively, any of layers 210-218 may be fabricated fromany material that enables system 200 to function as described herein. Inthe exemplary embodiment, layers 210-218 may be coupled to each otherusing any suitable fastening method that enables system 200 to functionas described herein. While seal member 204 is described as having amulti-layer laminated construction, in alternative embodiments, sealmember may have any number of layers that enables system 200 to functionas described herein.

In the exemplary embodiment, seal member 204 includes a layer 220 withseal end portions 222 and 224. In the exemplary embodiment, layer 220 isfabricated from any suitable material that enables system 200 tofunction as described herein. Specifically, layer 220 is fabricated froma sufficiently strong and flexible material that enables seal endportions 222 and 224 to resiliently bend to maintain contact with endwalls 226 and 228 of slot 208, and corresponding end walls (not shown)within slot 230 (shown in FIG. 4).

In the exemplary embodiment, seal member 204 includes both seal endportion 224 and seal end portion 222 (shown in broken lines). In analternative embodiment, seal member 204 may have only one of seal endportions 224 and 222. For example, in an alternative embodiment, sealend portion 222 may be omitted. In addition, in the exemplaryembodiment, seal end portions 222 and 224 both extend from the samelayer, for example, layer 220. In an alternative embodiment (not shown),seal end portions 222 and 224 may extend from different ones of layers210, 212, 214, 216, 218, and 220.

In the exemplary embodiment, seal end portion 224 is sized and orientedat an angle α with respect to a substantially planar web portion 223 oflayer 220. Seal end portion 222 is sized and oriented at an angle β,with respect to portion 223. In the exemplary embodiment, α and β havethe same value. In an alternative embodiment, each of α and β may haveany value that enables sealing system 200 to function as describedherein. After insertion of seal member 204 into slot 208, end edges 225and 227 of seal end portions 222 and 224 are maintained in contact withend walls 226 and 228, respectively. In the exemplary embodiment, sealend portions 222 and 224 extend integrally from substantially planar webportion 223. In an alternative embodiment, seal end portions 222 and 224are initially fabricated as discrete components that are subsequentlycoupled to substantially planar web portion 223 using any suitableattachment method that enables system 200 to function as describedherein.

In one embodiment, to facilitate assembly of system 200, seal member 204is initially fabricated with seal end portions 222 and 224 temporarilydeflected to positions 232 and 234 (illustrated in broken lines in FIG.3) and temporarily secured in position, for example via atemperature-sensitive adhesive 236, such that seal member 204 has aninitial overall length L that is shorter than a length M of slot 208, tofacilitate insertion of seal member 204 into slot 208. During turbineengine operation, adhesive 236 is exposed to elevated temperatures thatcause adhesive 236 to melt, enabling deployment of seal end portions 222and 224 to their extended positions, as illustrated in FIG. 3.

As illustrated in FIG. 4, seal member 204 provides a seal that extendsbetween adjacent components 202 and 203. More specifically, seal member204 spans a gap 205 defined between components 202 and 203. In theexemplary embodiment, a pressure in a cooler-temperature gas region 240is higher than a pressure in a hot gas path region 242 that is exposedto combustion gases. Accordingly, because of the pressure differentialbetween regions 240 and 242, during operation of gas turbine engine 100(shown in FIG. 1), seal member 204 is pressed against bottom walls 244and 246 of slots 208 and 230, respectively. By configuring seal endportions 222 and 224 to be resiliently flexible to maintain contact withend walls 226 and 228, sealing system 200 facilitates reducing orpreventing leakage around ends of seal member 204.

Seal member 204 is described and shown in FIGS. 2-4 as being received ina pair of adjacent slots 208 and 230 within adjacent turbine components202 and 203, wherein each of slots 208 and 230 receives and encircles aside of seal member 204. At least some known gas turbine engines 100(shown in FIG. 1), also include sealing systems that do not incorporatefully defined recesses such as slots 208 and 230. For example, FIG. 8illustrates an alternative sealing system 280 that may be used in gasturbine engine 100, with seal member 204 (shown in FIGS. 2-4). In theexemplary embodiment, sealing system 280 includes a plurality of shroudblocks 250 (of which two are shown in FIG. 8) that are arrangedcircumferentially within a gas turbine engine 100, with a seal member204 oriented between each adjacent pair of shroud blocks 250.

In the exemplary embodiment, shroud block 250 includes a flange 254 andan overlying flange 266. Flanges 254 and 266 are separated by a distanceH. At least a portion 262 of flange 254 is not covered by flange 266.Shroud block 250 also includes a flange 256 bounded by at least an endwall 258, and at least partially covered by a flange 268. In theexemplary embodiment, a similar end wall (not shown) is provided at anopposite end of flange 256. As previously described, seal members 204(shown in FIGS. 2-4) are oriented between each pair of adjacent shroudblocks 250. For example, a seal member 204 (not shown in FIG. 8) may beoriented between adjacent shroud blocks 250, such that it is supportedby flanges 256 and 256, and bounded at its ends by end wall 258 and acorresponding opposed end wall (not shown). In addition, the seal member204 is also maintained in position by flanges 268 and 266. Accordingly,flanges 254 and 266 define a first seal member receiving region 270, andflanges 256, 268, end wall 258 and an opposite end wall (not shown)define a second seal member receiving region 272. In the exemplaryembodiment, seal member receiving region 272 includes end wall 258 andan opposite end wall, while seal member region 270 does not include endwalls. In an alternative embodiment, each seal member region 270 and 272may include any number of end walls that enables sealing system 280 tofunction as described herein. For example, in an alternative embodiment,seal member region 272 may include end wall 258, while seal memberregion 270 may include an end wall (not shown) oriented at an end offlange 254 that is adjacent an end of flange 256 that is opposite to endwall 258.

Seal end portions 222 and 224 are shown in FIGS. 2-4 as substantiallyplanar, upwardly-angled elements. In alternative embodiments, other sealend portion configurations are provided. For example, FIG. 5 is a sidesectional view of an alternative exemplary sealing system 300 wherein aseal member 306 is received within a slot 304 in a static component 302.Seal member 306 is also inserted into a corresponding slot defined on anadjacent static component (not shown). In the exemplary embodiment, sealmember 306 is multi-layered, and includes a central seal layer 308.Upper layers 310 and 312 are coupled to central seal layer 308, as arelower layers 314 and 316. In the exemplary embodiment, any of layers308-316 may be fabricated from any suitable material that enablessealing system 300 to function as described herein. Moreover, layers308-316 may be coupled to each other using any suitable fastening methodthat enables system 300 to function as described herein. While sealmember 306 is described as having a multi-layer laminated construction,in alternative embodiments, seal member 306 may include any number oflayers that enables system 300 to function as described herein.

Seal member 306 includes seal end portions 318 and 322 that extend froma substantially planar web portion 328 of layer 308. In the exemplaryembodiment, each of seal end portions 318 and 322 has a “W”-shapedconfiguration. Moreover, seal end portions 318 and 322 are sized andconfigured to be resiliently flexible, such that after insertion of sealmember 306 into slot 304, seal end portion 318 is maintained in contactwith an end wall 320 of slot 304, and seal end portion 322 is maintainedin contact with an end wall 324 of slot 304. Furthermore, afterinsertion of seal member 306 into slot 304, one or both of seal endportions 318 and 322 is slightly compressed to provide a seal betweenseal end portions 318 and 322 and respective end walls 320 and 324.Accordingly, sealing system 300 facilitates reducing or preventingleakage around ends of seal member 306.

As described with respect to the embodiment of FIGS. 2-4, in oneembodiment, prior to assembly of system 300, seal end portions 318and/or 322 may be compressed or otherwise deflected, and temporarilyfastened in deflected positions, for example using atemperature-sensitive adhesive (not shown). Compression of seal endportions 318 and/or 322 facilitates insertion of seal member 306 intoslot 304, and into a corresponding slot (not shown) in an adjacentcomponent (not shown). After assembly, seal member 306 is exposed toengine operation temperatures that cause the adhesive to melt,facilitating subsequent deployment of seal end portions 318 and/or 322.

In the exemplary embodiment, a gas pressure of a purge gas in a region330 is higher than a gas pressure in a region 332. Accordingly, becauseof the pressure differential between regions 330 and 332 present duringturbine operation, seal member 306 is pressed against bottom wall 334 ofslot 304 and against a bottom wall of a corresponding slot in anadjacent component (not shown). Seal end portions 318 and 322 facilitatethe prevention of leakage of purge gas around seal member 306.

FIG. 6 is a side sectional view of another alternative exemplary sealingsystem 400. A seal member 406 is inserted within a slot 404 in a staticcomponent 402, and within a corresponding slot in an adjacent component(not shown). In the exemplary embodiment, seal member 406 ismulti-layered and includes seal layer 408 and layers 410, 412, and 414.Moreover, any of layers 408-414 may be fabricated from any suitablematerial that enables system 400 to function as described herein. Seallayer 408 includes a substantially planar web portion 409 from whichseal end portions 416 and 420 extend. Moreover, layers 408-416 may becoupled to each other using any suitable fastening method that enablessystem 400 to function as described herein. While seal member 406 isdescribed as having a multi-layer laminated construction, in alternativeembodiments, seal member 406 may include any number of layers thatenables system 400 to function as described herein.

In the exemplary embodiment, seal end portions 416 and 420 are arcuatein cross-section, and are configured to be resiliently flexible, suchthat after insertion of seal member 406, seal end portion 416 ismaintained in contact with an end wall 418 of slot 404, and seal endportion 420 is maintained in contact with an end wall 422 of slot 404.Furthermore, after insertion of seal member 406 into slot 404, one orboth of seal end portions 416 and 420 is slightly compressed to providea seal between seal end portions 416 and 420 and respective end walls418 and 422.

As described with respect to the embodiment of FIGS. 2-4, in oneembodiment, prior to assembly of system 400, one or both of seal endportions 416 and 420 may be compressed or otherwise deflected andtemporarily fastened in deflected positions, for example using atemperature-sensitive adhesive (not shown). Compression of seal endportions 416 and 420 facilitates insertion of seal member 406 into slot404 and into a corresponding slot in an adjacent component (not shown).After assembly, seal member 406 is exposed to engine operationtemperatures that cause the adhesive to melt, facilitating subsequentdeployment of seal end portions 416 and 420.

In the exemplary embodiment, a purge gas pressure in a region 430 ishigher than a gas pressure in a region 432. Accordingly, because of thepressure differential between regions 430 and 432 during turbineoperation, seal member 406 is maintained against bottom wall 434 of slot404 and against a bottom wall of a corresponding slot in an adjacentcomponent (not shown). Seal end portions 416 and 420 facilitate theprevention of purge gas leakage around seal member 406.

FIG. 7 is a side sectional view of another alternative exemplary sealingsystem 500. Seal member 506 is received within a slot 504 in a staticcomponent 502. Seal member 506 is also received within a correspondingslot in an adjacent static component (not shown). In the exemplaryembodiment, seal member 506 is multi-layered, and includes seal layers508 and 510, oriented between layers 512 and 514, and layers 516 and518. Furthermore, layers 508-518 may be coupled together using anysuitable fastening method that enables system 500 to function asdescribed herein. Moreover, in the exemplary embodiment, any of layers508-518 may be fabricated from any suitable material that enables system500 to function as described herein. While seal member 506 is describedas having a multi-layer laminated construction, in alternativeembodiments, seal member 506 may include any number of layers thatenables system 500 to function as described herein.

Seal end portions 520 and 526 extend from of layer 508. Seal endportions 522 and 528 extend from a substantially planar web portion 521of layer 510. In the exemplary embodiment, seal end portions 520, 522,526, and 528 are arcuate in cross-section, and are sized and configuredto be resiliently flexible, such that after insertion of seal member 506into slot 504, at least one of seal end portions 520, 522, 526, and 528is slightly compressed to provide a seal between seal end portions 520and/or 522 and end wall 524, and between seal end portions 526 and/or528 and end wall 536, respectively.

As described with respect to the embodiment of FIGS. 2-4, in oneembodiment, prior to assembly of system 500, at least one of seal endportions 520, 522, 526, and/or 528 is compressed or otherwise deflectedand temporarily fastened in a deflected position, for example using atemperature-sensitive adhesive (not shown). Compression of seal endportions 520, 522, 526, and/or 528 facilitates insertion of seal member506 into slot 504. After assembly, seal member 506 is exposed to engineoperation temperatures that cause the adhesive to melt, facilitatingsubsequent deployment of seal end portions 520, 522, 526, and/or 528.

In the exemplary embodiment, a purge gas pressure in a region 530 ishigher than a gas pressure in a region 532. Accordingly, because of thepressure differential between regions 530 and 532, during turbineoperation seal member 506 is maintained against bottom wall 534 of slot504 and against a bottom wall of a corresponding slot in an adjacentcomponent (not shown). Seal end portions 520, 522, 526, and/or 528facilitate the prevention of purge gas leakage around seal member 506.

In the embodiments of FIGS. 2, 5-7, seal members 204, 306, 406, and 506are each illustrated with seal end portions 222 and 224 (shown in FIG.2), 318 and 322 (shown in FIG. 5), 416 and 420 (shown in FIG. 6), and520, 522, 526, and 528 (shown in FIG. 7), wherein the seal end portionsin each embodiment have the same cross-sectional configuration. In analternative embodiment, the seal member end portions may have anyconfiguration, including different configurations at opposite ends of asingle seal member, that enables the sealing systems to function asdescribed herein. For example, in an alternative embodiment (not shown),a seal member may include a curved seal end portion at one end and a“W”-shaped seal end portion at an opposite end.

The subject matter described herein provides several advantages overknown methods of sealing between static components in a gas turbineengine. For example, the sealing systems described herein facilitatemaintaining a pressure boundary within a gas turbine engine between ahigher-temperature combustion gas path and a cooler-temperature gasregion, such as between an inner shell of a turbine and turbinecomponents directly exposed to combustion gases. The sealing systemsdescribed herein also facilitate reducing or preventing of leakagearound end regions of an elongated substantially planar (“spline”) sealmember. The system systems described herein also facilitate assembly ofturbine components by facilitating the temporary securement of seal endportions in deflected orientations, to facilitate insertion of the sealmembers into slots defined in adjacent turbine components. Moreover, thesealing systems described herein facilitates preventing excess outflowof high pressure purge through gaps defined between adjacent componentswithin a gas turbine engine and into the hot gas path, towardsfacilitating an increase in turbine efficiency.

Exemplary embodiments of a method and a system for providing sealingbetween static components of a gas turbine engine are described above indetail. The method and system are not limited to the specificembodiments described herein, but rather, components of systems and/orsteps of the methods may be utilized independently and separately fromother components and/or steps described herein. For example, the methodmay also be used in combination with other rotary machine systems andmethods, and are not limited to practice only with gas turbine enginesas described herein. Rather, the exemplary embodiment can be implementedand utilized in connection with many other rotary machine applications.

Although specific features of various embodiments of the claimed subjectmatter may be shown in some drawings and not in others, this is forconvenience only. In accordance with the principles of the subjectmatter described herein, any feature of a drawing may be referencedand/or claimed in combination with any feature of any other drawing.

This written description uses examples to disclose the claimed subjectmatter, including the best mode, and also to enable any person skilledin the art to practice the subject matter described herein, includingmaking and using any devices or systems and performing any incorporatedmethods. The patentable scope of the subject matter described herein isdefined by the claims, and may include other examples that occur tothose skilled in the art. Such other examples are intended to be withinthe scope of the claims if they have structural elements that do notdiffer from the literal language of the claims, or if they includeequivalent structural elements with insubstantial differences from theliteral language of the claims.

While the claimed subject matter has been described in terms of variousspecific embodiments, those skilled in the art will recognize that thesubject matter can be practiced with modification within the spirit andscope of the claims.

What is claimed is:
 1. A method for providing a seal between componentswithin a gas turbine, said method comprising: inserting a seal memberinto a first seal member receiving region defined within a firstcomponent of a gas turbine, wherein the first seal member receivingregion is oriented between a higher-temperature gas region and acooler-temperature gas region; and inserting the seal member into asecond recess defined within a second component of the gas turbine,wherein the second component is adjacent to the first component, andwherein at least one of the first and second seal member regionsincludes a first end wall and at least one of the first and second sealmember regions includes a second end wall oriented substantiallyopposite the first end wall, wherein the seal member includes at least afirst layer defining at least a first seal end portion that engages oneof the respective first and second end walls.
 2. The method inaccordance with claim 1, wherein said method further comprises definingthe seal member to include a second seal end portion that engagesanother of the first and second end walls.
 3. The method in accordancewith claim 2, wherein defining the seal member to include a second sealend portion further comprises defining the seal member to include firstand second seal end portions that have similar cross-sectionalconfigurations.
 4. The method in accordance with claim 2, whereindefining the seal member to include a second seal end portion furthercomprises defining the seal member to include first and second seal endportions that have different cross-sectional configurations.
 5. Themethod in accordance with claim 1, wherein said method further comprisesfabricating the seal member as a laminated seal member that includes atleast a second layer coupled to the first layer.
 6. The method inaccordance with claim 1, wherein said method further comprises definingthe first seal end portion as a planar member extending at an anglerelative to a planar web portion of the first layer.
 7. The method inaccordance with claim 1, wherein said method further comprises definingthe first seal end portion as a web extending from a planar web portionof the first layer, wherein the web includes a “W”-shapedcross-sectional configuration.
 8. The method in accordance with claim 1,wherein said method further comprises defining the first seal endportion as a web extending from a planar web portion of the first layer,wherein the web includes a curved cross-sectional configuration.
 9. Themethod in accordance with claim 1, wherein said method further comprisesdefining the seal member to include at least two layers, wherein each ofthe at least two layers includes at least one seal end portion.
 10. Themethod in accordance with claim 9, wherein defining the seal member toinclude at least two layers further comprises defining each of the atleast two layers to include first and second seal end portions havingsimilar cross-sectional configurations.
 11. A gas turbine system, saidsystem comprising: a compressor section; a combustor assembly coupled tosaid compressor section; and a turbine section coupled to saidcompressor section, wherein at least one of said combustor assembly andsaid turbine section includes a sealing sub-system for use in sealingbetween a first component and a second component, said sealingsub-system comprises: a first component defining a first seal memberreceiving region oriented between a higher-temperature gas region and acooler-temperature gas region; a second component adjacent said firstcomponent, said second component defining a second seal member receivingregion oriented adjacent said first seal member receiving region,wherein at least one of said first and second seal member receivingregions includes a first end wall, and at least one of said first andsecond seal member receiving regions includes a second end wall orientedsubstantially opposite said first end wall; and a seal member orientedwithin said first and second seal member receiving regions, wherein saidseal member includes at least a first layer defining at least a firstresilient seal end portion that engages one of said first and second endwalls.
 12. The gas turbine system in accordance with claim 11, whereinsaid seal member includes a second seal end portion that engages anotherof said first and second end walls.
 13. The gas turbine system inaccordance with claim 12, wherein said first and second portions includesimilar cross-sectional configurations.
 14. The gas turbine system inaccordance with claim 12, wherein said first and second seal endportions include different cross-sectional configurations.
 15. The gasturbine system in accordance with claim 11, wherein said seal member isa laminated seal member that includes at least a second layer coupled tothe first layer.
 16. The gas turbine system in accordance with claim 11,wherein said first seal end portion comprises a planar member extendingat an angle relative to a planar web portion of said first layer. 17.The gas turbine system in accordance with claim 11, wherein said firstseal end portion comprises a web extending from a planar web portion ofsaid first layer, wherein said web includes a “W”-shaped cross-sectionalconfiguration.
 18. The gas turbine system in accordance with claim 11,wherein said first seal end portion comprises a web extending from aplanar web portion of said first layer, wherein said web includes acurved cross-sectional configuration.
 19. The gas turbine system inaccordance with claim 11, wherein said seal member comprises at leasttwo layers, wherein each of said at least two layers includes at leastone seal end portion.
 20. The gas turbine system in accordance withclaim 19, wherein each of said at least two layers comprises first andsecond seal end portions having similar cross-sectional configurations.